Double-side support balance structure for measuring influence of intake and exhaust

Abstract

The invention discloses a bilateral support balance structure for measuring intake and exhaust influence, and belongs to the field of aerodynamics. The device comprises an aircraft fuselage shell, an air inlet channel upper cover, a double-support balance, a corrugated pipe and a fixed support, the double-support balance comprises a front shell matching section, a front air inlet channel, an air inlet channel lower cover, support balances and a rear shell matching section, the aircraft fuselage shell is connected with the double-support balance through the shell matching section, the air inlet channel lower cover is connected with the front shell matching section, and the two sides of the front shell matching section and the two sides of the rear shell matching section are connected through the support balances. The air inlet channel lower cover is provided with an air inlet channel upper cover, the air inlet channel upper cover and the air inlet channel lower cover jointly form a middle air inlet channel, the rear shell matching section is provided with a fixed support, and the rear air inlet channel of the rear shell matching section is communicated with the air inlet passage through a corrugated pipe. The problems that a complete air inlet channel is formed in the middle of an aircraft wing body, the internal space is narrow, a balance cannot be installed, and the six-component load measurement requirement cannot be met are solved.

Description

Technical Field

[0001] The invention relates to a double-side supported balance structure for measuring the influence of intake and exhaust, and belongs to the field of aerodynamics. Background Art

[0002] Wind tunnel force measurement test is the most basic test item in wind tunnel test, and wind tunnel balance is the direct measurement equipment of aerodynamic load. In the process of aircraft development, the intake and exhaust of the aircraft will directly affect its aerodynamic performance. The air intake is the interface of the aircraft propulsion system, and the influence of the intake effect on the lift surface flow is particularly obvious. Through the intake and exhaust effect wind tunnel test, the influence of the intake and exhaust on the aerodynamic performance of the whole aircraft can be obtained.

[0003] Most modern aircrafts have a flat layout and a large lift surface, but the middle part of the fuselage is occupied by the air intake, which leaves insufficient space for the balance installation. Therefore, the present invention proposes a double-sided support balance structure for measuring the effects of intake and exhaust, which can achieve high-precision measurement of the load in the aircraft intake and exhaust effect wind tunnel test. Summary of the invention

[0004] The purpose of the present invention is to solve the problem that there is a complete air inlet in the middle of the wing of the aircraft, the internal space is small, the balance cannot be installed, and the measurement requirements of the six-component load cannot be met. A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to determine the key or important parts of the present invention, nor is it intended to limit the scope of the present invention.

[0005] The technical solution of the present invention: A double-side support balance structure for measuring the impact of intake and exhaust, comprising an aircraft fuselage shell, an intake duct upper cover, a double-support balance, a bellows and a fixed support; The double-support balance comprises a front shell matching section, a front air inlet, an air inlet lower cover, a support balance and a rear shell matching section. The aircraft fuselage shell and the double-support balance are connected and installed through the front shell matching section. The front side of the air inlet lower cover is connected to the rear side of the front shell matching section. The left and right sides of the front shell matching section and the rear shell matching section are both connected through the support balance. The support balance is symmetrically arranged on both sides of the air path as a double support. An air inlet upper cover is installed on the top of the air inlet lower cover. The air inlet upper cover and the air inlet lower cover jointly form a middle air inlet. The front air inlet is connected to the middle air inlet. A rear air inlet is arranged inside the rear shell matching section. A fixed support is installed at the bottom of the rear shell matching section. A bellows is installed between the air inlet upper cover and the rear shell matching section. A vent is processed on the fixed support. The front end of the rear air inlet is connected to the middle air inlet through the bellows, and the rear end of the rear air inlet is connected to the vent.

[0006] Preferably: a fixed end assembly surface is arranged at the bottom of the rear shell matching section, an assembly surface is processed on the fixed support, and the fixed support and the rear shell matching section are matched through the fixed end assembly surface and the assembly surface.

[0007] Preferably: a sealing ring is provided at the matching position between the rear air inlet and the air vent.

[0008] Preferably, the bellows is provided with a front flange and a rear flange at the front and rear sides respectively, the front flange is fixedly connected to the rear ends of the air inlet upper cover and the air inlet lower cover, and the rear flange is fixedly connected to the front end of the rear shell mating section.

[0009] Preferably, the front air intake duct, the middle air intake duct, the bellows, the rear air intake duct and the air vents together constitute an air intake and exhaust passage.

[0010] Preferably, there are at least two exhaust passages.

[0011] The present invention has the following beneficial effects: 1. The bellows structure adopted in the present invention connects the rear air intake duct and the air intake passage, thereby avoiding affecting the rigidity of the supporting balance and realizing the ventilation function; 2. The present invention can realize the measurement of intake effect and exhaust effect respectively by changing the blocking position of the front and rear air intake ducts of the supporting balance; adopt the method of front air intake and rear blocking to realize the measurement of intake effect; when the front is blocked and the rear is ventilated, the measurement of exhaust effect can be realized; 3. The present invention integrates the balance with the aircraft air inlet and shape to form a fusion balance, which realizes the six-component aerodynamic load measurement of the aircraft with a flat layout and a central air inlet structure in a limited space; 4. The double-support balance of the present invention is arranged on both sides of the air inlet duct, symmetrical along the neutral plane, and the load is measured without eccentricity. The strain gauge pasting position is arranged at the same cross section in front and back, and the strain gauges are bridged at the same cross section to eliminate the internal stress of the front and back temperature gradient. The double-support balance on the left and right sides is combined to improve the accuracy of the balance; 5. The present invention adopts a frame-type double-support structure as a whole, and uses the outer shape to close the double-support balance front and back, which has strong overall rigidity. Compared with the split-structure double-support, it reduces the installation repeatability error and ensures the repeatability of different period tests; 6. The present invention adopts a calibration method with fuselage loading. Different from the conventional balance calibration in which the balance body is calibrated and then installed for testing, the present invention simulates the actual measurement state after the fuselage, bellows, etc. are fully assembled, and the assembly stress of the bellows, etc. is converted into internal force, which is eliminated during calibration, thereby improving the test measurement accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a front view of a double-side supported balance structure for measuring the influence of intake and exhaust; Figure 2 It is a three-dimensional diagram of a double-sided support balance structure for measuring the influence of intake and exhaust; Figure 3 It is a coordination installation diagram of a double-sided support balance structure for measuring the influence of intake and exhaust; Figure 4 yes Figure 1 AA section view; Figure 5 It is a diagram of the coordinated installation of the air inlet cover and the double-support balance of the present invention; Figure 6 It is a diagram of the coordinated installation of the fixed support and double support balance of the present invention; Figure 7 It is a schematic structural diagram of a double-support balance of the present invention; Figure 8 is a three-dimensional diagram of the bellows of the present invention; Fig. 9 is a three-dimensional diagram of a fixed support of the present invention; Fig.10 is a three-dimensional diagram of the air inlet cover of the present invention; In the figure, 1-aircraft fuselage shell, 2-air inlet upper cover, 3-double support balance, 4-bellows, 5-fixed support, 31-front shell matching section, 32-front air inlet, 33-air inlet lower cover, 34-support balance, 35-rear shell matching section, 36-middle air inlet, 37-rear air inlet, 41-front flange, 42-rear flange, 51-vent, 52-assembly surface, 53-sealing ring. DETAILED DESCRIPTION

[0013] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0014] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection is a non-detachable connection including but not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but not limited to conventional detachable methods such as threaded connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can always be found in the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example: a fixed connection is selected as a welding connection, and a detachable connection is selected as a hinge connection.

[0015] Specific implementation method 1: Combination Figure 1-Figure 10The present embodiment is described. The present embodiment is a double-side support balance structure for measuring the impact of air intake and exhaust gas, comprising an aircraft fuselage shell 1, an air intake cover 2, a double-support balance 3, a bellows 4 and a fixed support 5; The double support balance 3 comprises a front shell matching section 31, a front air inlet 32, an air inlet lower cover 33, a support balance 34 and a rear shell matching section 35. The aircraft fuselage shell 1 and the double support balance 3 are connected and installed via the front shell matching section 31. The front side of the air inlet lower cover 33 is connected to the rear side of the front shell matching section 31. The left and right sides of the front shell matching section 31 and the rear shell matching section 35 are both connected via the support balance 34. The support balance 34 is symmetrically arranged on both sides of the air path as a double support. The air inlet lower cover 33 is installed on the top of the air inlet. The upper cover 2, the air inlet upper cover 2 and the air inlet lower cover 33 together form the middle air inlet 36, the front air inlet 32 ​​is connected with the middle air inlet 36, the rear shell matching section 35 is provided with the rear air inlet 37, the bottom of the rear shell matching section 35 is installed with a fixed support 5, the bellows 4 is installed between the air inlet upper cover 2 and the rear shell matching section 35, the fixed support 5 is processed with a vent 51, the front end of the rear air inlet 37 is connected with the middle air inlet 36 through the bellows 4, and the rear end of the rear air inlet 37 is connected with the vent 51. The overall structure of the aircraft fuselage shell 1, the air inlet upper cover 2, the double support balance 3, the bellows 4 and the fixed support 5 is closed front and back, and the strain gauges are attached to the support balances 34 on the left and right sides to realize the measurement of the six-component load, and the joint bridge on both sides is used to reduce the influence of the internal stress of the assembly.

[0016] The front shell matching section 31 and the air inlet duct lower cover 33 are integrally formed, and a gap for installing a bellows is reserved between the air inlet duct lower cover 33 and the rear shell matching section 35 .

[0017] The bottom of the rear shell matching section 35 is provided with a fixed end assembly surface, and the fixed support 5 is processed with an assembly surface 52 . The fixed support 5 and the rear shell matching section 35 are matched through the fixed end assembly surface and the assembly surface 52 .

[0018] A sealing ring 53 is provided at the joint between the rear air inlet 37 and the vent hole 51 for sealing.

[0019] The front air inlet 32, the middle air inlet 36, the bellows 4, the rear air inlet 37 and the vent 51 together constitute an air inlet and exhaust passage, which diverts the air of the front air inlet 32. There are at least two exhaust passages.

[0020] The bellows 4 is provided with a front flange 41 and a rear flange 42 on the front and rear sides respectively. The front flange 41 is fixedly connected to the rear ends of the air inlet upper cover 2 and the air inlet lower cover 33, and the rear flange 42 is fixedly connected to the front end of the rear shell mating section 35. The middle of each intake and exhaust channel is connected by a bellows 4. The bellows 4 eliminates the influence of the bellows stiffness on the measurement of the supporting balance 34, and at the same time seals the airflow passing through the intake and exhaust channels to prevent air leakage.

[0021] When a double-sided support balance structure for measuring the impact of intake and exhaust in this embodiment is used for a force measurement test, the specific method is as follows: Combination Figure 7 : First, complete the pasting of the support balance 34, calibrate the body of the support balance 34, and then install the overall structure; Combination Figure 7-10 During installation, first install the air inlet cover 2 and the double-support balance 3, then compress the two bellows 4 and put them into the corresponding positions on both sides, then loosen them, and tighten the front flange 41 and the rear flange 42.

[0022] Combination Figure 2-10 : Install the sealing ring 53 on the fixed support 5, assemble it with the installed double-support balance 3, complete the installation of the overall device, calibrate the installed structure as a whole, eliminate the influence of various assembly parts and bellows 4 on the double-support balance 3, and ensure the accuracy of the measurement results.

[0023] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be arranged and combined, and those skilled in the art can exhaust all possibilities based on the mathematical knowledge of arrangement and combination. Therefore, the present invention will no longer describe the technical solutions after arrangement and combination one by one, but it should be understood that the technical solutions after arrangement and combination have been disclosed by the present invention.

[0024] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A double-sided support balance structure for measuring the influence of intake and exhaust, characterized in that: It comprises an aircraft fuselage shell (1), an air inlet cover (2), a double-support balance (3), a bellows (4) and a fixed support (5); The double support balance (3) comprises a front shell matching section (31), a front air inlet (32), an air inlet lower cover (33), a support balance (34) and a rear shell matching section (35). The aircraft fuselage shell (1) and the double support balance (3) are connected and installed via the front shell matching section (31). The front side of the air inlet lower cover (33) is connected to the rear side of the front shell matching section (31). The left and right sides of the front shell matching section (31) and the rear shell matching section (35) are both connected via the support balance (34). The support balance (34) is symmetrically arranged on both sides of the air path as a double support. The air inlet upper cover (20) is installed on the top of the air inlet lower cover (33). ), the air inlet duct upper cover (2) and the air inlet duct lower cover (33) together form a middle air inlet duct (36), the front air inlet duct (32) is connected to the middle air inlet duct (36), a rear air inlet duct (37) is arranged inside the rear shell matching section (35), a fixed support (5) is installed at the bottom of the rear shell matching section (35), a bellows (4) is installed between the air inlet duct upper cover (2) and the rear shell matching section (35), a vent hole (51) is processed on the fixed support (5), the front end of the rear air inlet duct (37) is connected to the middle air inlet duct (36) through the bellows (4), and the rear end of the rear air inlet duct (37) is connected to the vent hole (51).

2. The double-sided support balance structure for measuring the influence of intake and exhaust according to claim 1, characterized in that: The bottom of the rear shell matching section (35) is provided with a fixed end assembly surface, the fixed support (5) is processed with an assembly surface (52), and the fixed support (5) and the rear shell matching section (35) are matched via the fixed end assembly surface and the assembly surface (52).

3. The double-sided support balance structure for measuring the influence of intake and exhaust according to claim 2, characterized in that: A sealing ring (53) is provided at the joint between the rear air inlet (37) and the vent hole (51).

4. The double-sided support balance structure for measuring the influence of intake and exhaust according to claim 3, characterized in that: The bellows (4) is provided with a front flange (41) and a rear flange (42) at the front and rear sides respectively; the front flange (41) is fixedly connected to the rear ends of the air inlet duct upper cover (2) and the air inlet duct lower cover (33); and the rear flange (42) is fixedly connected to the front end of the rear shell mating section (35).

5. A double-sided support balance structure for measuring the influence of intake and exhaust according to any one of claims 1 to 4, characterized in that: The front air intake duct (32), the middle air intake duct (36), the bellows (4), the rear air intake duct (37) and the vent hole (51) together constitute an air intake and exhaust passage.

6. The double-sided support balance structure for measuring the influence of intake and exhaust according to claim 5, characterized in that: There are at least two exhaust passages.

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